Component bonding method and structure

Abstract

A method of bonding two components at a joint interface using a UV-curable substance. The method comprises incorporating a UV radiation emitting device in the joint interface between the components together with said substance and supplying power to said UV radiation emitting device to generate UV radiation and cure the substance.

Claims

1. A method of bonding two components at a joint interface using a UV-curable substance, comprising: embedding a UV radiation emitting device in the joint interface together with said substance, wherein the UV radiation emitting device comprises a plurality of spaced UV radiation elements, forming the plurality of UV radiation emitting elements in a grid having spaces between the UV radiation emitting elements, and activating said UV radiation emitting device by supplying power wirelessly by induction to said UV radiation emitting device incorporated in the joint interface to generate UV radiation by the UV radiation emitting device and cure the substance with the UV radiation.

2. The method of separating components bonded according to the method of claim 1 comprising re-activating the UV radiation emitting device for a period of time sufficient to cause the previously cured substance to degrade.

3. An aircraft wing comprising the components bonded using the method according to claim 1.

4. A structure comprising two components bonded to each other at a joint interface using a UV curable substance, comprising a UV radiation emitting device embedded in said joint interface which has been activated wirelessly by induction to generate UV radiation to cure the substance, wherein the UV radiation emitting device comprises a plurality of spaced UV radiation elements, and wherein the plurality of UV radiation emitting elements is formed in a grid having spaces between the UV radiation emitting elements.

5. The structure according to claim 4, wherein the spaces include holes or gaps therebetween through which the substance can flow.

6. The structure according to claim 4, wherein said UV radiation emitting elements are OLED's.

7. The structure according to claim 4, wherein said UV curable substance is an adhesive.

8. The structure according to claim 4, wherein said UV curable substance is a sealant.

9. The structure according to claim 4, wherein said components comprise parts of an aircraft wing.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1 shows a schematic view of a UV light generating device embedded in a joint interface between two substrates, according to an embodiment of the invention.

(2) FIG. 2 shows a schematic view of a UV light generating device embedded in a joint interface between two substrate, according to at least one embodiment of the invention.

DETAILED DESCRIPTION OF THE EMBODIMENTS

(3) FIG. 1 shows two components, each having a substrate 1, 2 joined at a joint interface 3 using an ultra violet (UV) curable substance such as an adhesive or sealant 4. A UV radiation emitting device 5 is embedded in the substance 4 in the joint interface 3.

(4) The UV radiation emitting device 5 can comprise a number of separate UV light emitting elements 5a or OLED's (Organic Light Emitting Devices). Preferably, the elements 5a are arranged on a grid or other mat or framework 6, but have holes, gaps or spaces 7 between them to allow the substance 4 to flow through and around the device 5 and thereby bond the substrates 1, 2 together without acting as a barrier between the bondable surfaces. The elements 5a are all connected to each other electrically.

(5) Wires 8, 9 extend from the device 5 so that power may be supplied to all of the elements sa from a power source 10.

(6) When two components are to be bonded, one or both substrates 1, 2 are coated with the UV curable adhesive 4 at the joint interface and the LTV radiation emitting device 5 is embedded in the adhesive 4. The components are then brought together and clamped in the required position. Power is then supplied to the elements 5a for a predetermined period of time so that they generate UV radiation sufficient to cure the UV curable adhesive 4. Once curing is complete, the power source 10 may be disconnected and the wires may be cut off. The UV radiation emitting device remains embedded in the bonded components.

(7) In an alternate embodiment, power may be supplied to the device 5 wirelessly via an induction coil 12, as seen in FIG. 2, or the UV light emitting device may be activated in some other way.

(8) Although a number of different UV radiation emitting devices may be used, OLED's are preferred as they have a thin geometry, are of low cost, have low energy consumption and are robust and flexible.

(9) The components being joined may form part of an aircraft wing, as joints of this type are easier to make and much lighter than using nuts and bolts to connect components together.

(10) In addition to bonding two components, it is also envisaged that components that have been bonded with a UV emitting device embedded in the joint interface can also be separated more easily by activating the UV emitting device for a prolonged length of time sufficient to cause the cured UV adhesive to degrade.

(11) It will be appreciated that the foregoing description is given by way of example only and that modifications may be made to the support assembly of the present invention without departing from the scope of the appended claims.